CN102011026A - Titanium alloy used for aviation fastener and manufacturing method - Google Patents
Titanium alloy used for aviation fastener and manufacturing method Download PDFInfo
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Abstract
The invention discloses a titanium alloy used for an aviation fastener and a manufacturing method, and relates to a titanium base alloy. The titanium alloy comprises the following elements in percentage by mass: 5 to 9 percent of aluminum (Al), 1 to 6 percent of vanadium (V), 8 percent of molybdenum (Mo), 11 to 15 percent of niobium (Nb), 1 percent of zirconium (Zr), 0.1 to 2 percent of chromium (Cr) and the balance of Ti, wherein an amorphous titanium alloy inoculant is added in a melting process of the titanium alloy. The titanium alloy used for the aviation fastener has more reasonable new element compositions; the amorphous titanium alloy inoculant is added into the melting process; a heterogeneous nucleation core when the titanium alloy is solidified is added; the crystal size of an as-cast titanium alloy is refined; the tensile strength of a titanium alloy product used for the aviation fastener manufactured by the manufacturing method for the titanium alloy used for the aviation fastener can reach 1,370 MPa; the elongation rate can reach 11.6 percent; and the titanium alloy has both strength and flexibility and can be widely used for fasteners for manufacturing a civil aviation aircraft.
Description
Technical field
Technical scheme of the present invention relates to titanium base alloy, specifically aviation fastening piece titanium alloy and preparation method thereof.
Background technology
Along with the quickening of domestic and international military-civil machine update and improving constantly of aeroplane performance requirement, aircraft structure is harsh more with the material condition, the material of an urgent demand good combination property.The over-all properties of titanium enjoys airplane design person's favor, and consumption aboard constantly rises.Aircraft industry is the staple market of titanium alloy, and at present, about in the world 3/4 titanium alloy is used for aerospace and war products.Titanium alloy is used to manufacture general structural part, subassembly and the fastening piece of aircraft, even manufactures large-scale integral structure component.
The existing aircraft of China only is 2%～3% with the titanium amount, has a long way to go with abroad comparing.Although material department is carried out the research of titanium alloy already, and satisfied certain needs of aviation design application department, generally speaking, the China's titanium alloy still is in the stage that research is many, application is few.Improve the structure benefit of aircraft, enlarge the application of titanium alloy on China's aircraft structure, shorten and external gap, need to strengthen the research and the aerospace applications of titanium alloy.
CN101343706 discloses a kind of beta titanium alloy for fastener and preparation method, and its preparation method is the employing titanium sponge, fine aluminium, and pure chromium, Ti-31%Mo, Ti-53%Nb behind the Al-80%Ta batch mixing, is pressed into block electrode with press; The several piece electrode is welded into the strip electrode with the ion soldering group in vacuum consumable electrode arc furnace, carries out melting, again the ingot casting that obtains is carried out melting 2～3 times once more as consumable electrode, obtain the product titanium alloy ingot as consumable electrode.CN101314827 discloses a kind of beta titanium alloy and preparation method thereof, and its preparation method is the employing titanium sponge, fine aluminium, and zirconium sponge is made consumable electrode behind Ti-31%Mo, Ti-53%Nb, the Al-80%Ta batch mixing; Obtain an ingot casting through the vacuum consumable electrode arc furnace melting; Carry out melting by an ingot casting as consumable electrode and obtain the secondary ingot casting; Become the product titanium alloy ingot by the secondary ingot casting as the consumable electrode vacuum consumable smelting.
Existing commonly used fastening piece often can not have both higher intensity and plasticity preferably with titanium alloy.For example, the tensile strength of the titanium alloy VT22 that often uses is 1160MPa at present, and unit elongation is 4.2%; The tensile strength of titanium alloy T i-15-3 is 840MPa, and unit elongation is 21%; The tensile strength of titanium alloy beta 21S is 1015MPa, and unit elongation is 17%; The tensile strength of TIMETALLCB is 1095MPa, and unit elongation is 17%.At present these well-known titanium alloys and the beta-titanium alloy that adopts above-mentioned existing patented technology to make all exist to have higher-strength and do not have good plasticity again, perhaps have the shortcoming that plasticity does not preferably have intensity fully up to expectations again.
In addition, the method that present people prepare titanium alloy mainly is first melting, forges again, carries out suitable solution treatment and ageing treatment at last.With the titanium alloy that this kind method is made, the raising of its over-all properties is limited really.
Summary of the invention
Technical problem to be solved by this invention is: aviation fastening piece titanium alloy and preparation method thereof is provided, this aviation fastening piece has new rational more elementary composition composition with titanium alloy, and in the fusion process of this titanium alloy, add the amorphous titanium alloy nucleating agent, the aviation fastening piece that makes thus has both higher intensity and plasticity preferably simultaneously with titanium alloy, has satisfied the requirement of high strength and high tenacity.
The present invention solves this technical problem the technical scheme that is adopted:
Aviation fastening piece titanium alloy, its elementary composition mass percent are that Al:5%～9%, V:1%～6%, Mo:8%, Nb:11%～15%, Zr:1%, Cr:0.1%～2% and surplus are Ti.
The above-mentioned aviation fastening piece preparation method of titanium alloy, its step is as follows:
The first step, preparation amorphous titanium alloy nucleating agent
(1) raw material of configuration preparation amorphous titanium alloy nucleating agent
Mass percent by element is that Cu:10%～15%, Ni:10%～15%, Al:1%～5%, V:1%～5%, Fe:3%～10%, B:1%～5%, Zr:5%～10%, Cr:1%～5% and surplus are the raw material of Ti configuration preparation amorphous titanium alloy nucleating agent;
(2) melting
(1) step confected materials is put into the water jacketed copper crucible of non-consumable arc furnace, regulate the tungsten electrode position, make it and water jacketed copper crucible in distance between the amorphous titanium alloy nucleating agent raw material put into be 0.5mm～1.5mm, close fire door and purging valve, be evacuated to vacuum tightness force value＞2 * 10
-2Behind the Pa; charging into high-purity argon gas to the force value of vacuum tightness subsequently is 0.06Pa～0.08Pa; regulate arc current after the starting the arc and progressively rise to 200A～300A; whole process is all protected with high-purity argon gas; to all raw material fusings; cool to room temperature with the furnace; obtain titan alloy casting ingot; again with the above-mentioned repeatedly fusing and be cooled to the smelting operation process 4 times～6 times of room temperature in water jacketed copper crucible of gained titan alloy casting ingot; obtain composition titan alloy casting ingot relatively uniformly, the uniform relatively titan alloy casting ingot of this composition is being evacuated to vacuum tightness＞2 * 10
-3In 900 ℃～1100 ℃ equalizing temperature annealing 7h～10h, make the titan alloy casting ingot of the complete homogenizing of composition in the vacuum annealing furnace of Pa;
(3) centrifugal fast quenching gets rid of band
The titan alloy casting ingot line that (2) is gone on foot the complete homogenizing of composition that makes cuts into fritter, put into the water jacketed copper crucible of vacuum quick quenching furnace, regulate electrode position, make it and water jacketed copper crucible in the titan alloy casting ingot fritter between distance be 1.5mm, close fire door, feed inlet and outlet and purging valve, be evacuated to vacuum tightness force value＞5 * 10
-3Behind the Pa, use ar purging, charging into argon gas to the force value of vacuum tightness subsequently is 0.05Pa, regulate arc current after the starting the arc and progressively rise to 600A, the titan alloy casting ingot fritter is melted, when treating that this titanium alloy fritter all is fused into liquid state, the inclination crucible makes titanium alloy liquid cause on the water-cooled molybdenum wheel of high speed rotating by runner, and the molybdenum wheel surface is 15 ℃, after the fused solution titanium alloy is in contact with it, rapid solidification, molybdenum wheel edge line speed is 50m/ second, and titanium alloy forms thin ribbon shaped and flown out by molybdenum wheel tangential direction, falls into the boxroom of body of heater bottom after baffle plate stops, fast quenching obtains the amorphous titanium alloy band, is the amorphous titanium alloy nucleating agent;
Second step, the preparation of titanium alloy product of aviation fastening piece
(1) configuration titanium alloy substrate raw material
With pure titanium, pure molybdenum, niobium bar, zirconium sponge, pure chromium, fine aluminium and pure vanadium is raw material, amount also by mass percentage for Al:5%～9%, V:1%～6%, Mo:8%, Nb:11%～15%, Zr:1%, Cr:0.1%～2% and surplus are that Ti takes by weighing above-mentioned all raw materials, is configured to the titanium alloy substrate raw material according to actual needs;
(2) melting and casting
Earlier with the pure titanium, pure molybdenum and the niobium bar raw material that take by weighing in (1) step, by weight being Nb: Ti=4: 1 niobium bar and pure titanium and Mo: Ti=4: 1 pure molybdenum and pure titanium are smelted into NbTi master alloy and MoTi master alloy respectively, and again other all raw materials that take by weighing in (1) step are put into the vacuum shower furnace with above-mentioned NbTi master alloy and MoTi master alloy and carry out following smelting operation: earlier the vacuum shower furnace being pumped into high vacuum pressure before the melting is 1.2 * 10
-4Pa～2.7 * 10
-4Pa, charging into argon gas to vacuum shower furnace internal pressure again is 0.1Pa～0.5Pa, protects, to all raw material fusings, cool to room temperature with the furnace, obtain titan alloy casting ingot, above-mentioned repeatedly fusing and be cooled to the smelting operation 4～6 times of room temperature adds weight during smelting operation and is 0.4% the amorphous titanium alloy nucleating agent that is made by the first step of titanium alloy substrate raw material gross weight the last time, cast then, after treating that titanium alloy cools off fully, prepared titan alloy casting ingot is taken out in blow-on;
(3) forge
To forge at 900 ℃～1100 ℃ by prepared titan alloy casting ingot of (2) step, reach deflection and be 70%～120% after water-cooled immediately, the deformation of preserving material internal makes and forges the titanium alloy sample of finishing;
(4) water-cooled insulation makes aviation fastening piece titanium alloy product
To put into vacuum tube furnace by the titanium alloy sample that the forging that (3) step makes is finished, be evacuated to vacuum tightness＜0.33Pa, water-cooled is to room temperature behind 700 ℃～950 ℃ insulation 20min, again this sample is incubated 0.5h～5h at 400 ℃～550 ℃, making elementary composition mass percent is that Al:5%～9%, V:1%～6%, Mo:8%, Nb:11%～15%, Zr:1%, Cr:0.1%～2% and surplus are the aviation fastening piece titanium alloy product of Ti.
The above-mentioned aviation fastening piece preparation method of titanium alloy, the section area of the sample before described deflection=(section area of the sample after the section area-forging of the sample before forging)/forging.
Above-mentioned aviation fastening piece is with the preparation method of titanium alloy, and related raw material, technology and equipment all are that metallurgical technology field is known and know.
The invention has the beneficial effects as follows: compared with prior art, aviation fastening piece of the present invention is as follows with the advantage of titanium alloy and preparation method thereof:
I. the present invention has outstanding substantive distinguishing features
Aviation fastening piece of the present invention has new rational more elementary composition composition with titanium alloy; The present invention at preparation aviation fastening piece with the technologic innovation of titanium alloy is: in melting technology, added the amorphous titanium alloy nucleating agent, increased the heterogeneous forming core core when titanium alloy solidifies, refinement as cast condition titanium alloy crystal grain.On this basis, forge again and solid solution, the comprehensive mechanical property of fastening piece titanium alloy material is significantly improved.Theoretically, the amorphous titanium alloy nucleating agent is to obtain under the rapid solidification condition, the surface energy of amorphous titanium alloy nucleating agent band is very high, the surface atom scission of link is many, be easy to fuse into the matrix melts of titanium alloy fast, and uniform distribution in the matrix melts of titanium alloy fast, compare with other nucleating agents, not only increased the heterogeneous forming core core when titanium alloy solidifies, and made the grain refining of whole as cast condition titanium alloy more even.
II. marked improvement of the present invention
(1) strength and toughness of titanium alloy product of the present invention has both
The prior art for preparing fastening piece is not with adding the amorphous titanium alloy nucleating agent in the titanium alloy technology, by the solid solution and the prepared fastening piece titanium alloy product of two-phase region timeliness of single phase region, tensile strength can only reach 1230Mpa, unit elongation 10.5% thus.Adopt the preparation method of aviation fastening piece of the present invention with titanium alloy, after adding the amorphous titanium alloy nucleating agent, the refinement of titanium alloy product grain-size is obvious, under the situation that does not reduce titanium alloy product material plasticity, has improved the tensile strength of titanium alloy product material.The drawn test, the aviation fastening piece that makes with the preparation method of titanium alloy with aviation fastening piece of the present invention can reach 1370Mpa with the tensile strength of titanium alloy product, unit elongation can reach 11.6%, tough having both, can be widely used in manufacturing the fastening piece of civil aviation aircraft.
(2) cost of titanium alloy product of the present invention reduces
Aviation fastening piece of the present invention has carried out autonomous innovation with titanium alloy on composition, and does not select the comparatively expensive metallic element of price for use, and for example tantalum has reduced cost, has created economic benefit.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is the aviation fastening piece that does not add the refinement of amorphous nucleating agent titanium alloy as cast condition metallographic structure photo.
Fig. 2 is the aviation fastening piece of the present invention that adds the refinement of amorphous nucleating agent titanium alloy as cast condition metallographic structure photo.
Embodiment
Found out that by Fig. 1 the aviation fastening piece that does not add the refinement of amorphous nucleating agent is about 200～400 μ m with the grain-size of as cast condition titanium alloy, grain-size is bigger.
Found out that by Fig. 2 the aviation fastening piece of the present invention of adding amorphous nucleating agent refinement is about 50～120 μ m with the grain-size of as cast condition titanium alloy, grain-size obviously diminishes.
Comparison diagram 1 and Fig. 2 are as seen, owing in the melting technology of aviation fastening piece of the present invention, added the amorphous titanium alloy nucleating agent with the preparation method of titanium alloy, increased the heterogeneous forming core core when titanium alloy solidifies, refinement as cast condition titanium alloy crystal grain, on this basis, forge again and solid solution, make the comprehensive mechanical property of aviation fastening piece titanium alloy material of the present invention be significantly improved.
Embodiment 1
Preparing elementary composition mass percent is that Al:5%, V:6%, Mo:8%, Nb:11%, Zr:1%, Cr:2% and surplus are the aviation fastening piece titanium alloy of Ti, and its step is as follows:
The first step, preparation amorphous titanium alloy nucleating agent
(1) raw material of configuration preparation amorphous titanium alloy nucleating agent
Mass percent by element is that Cu:10%, Ni:15%, Al:1%, V:5%, Fe:3%, B:5%, Zr:5%, Cr:5% and surplus are the raw material of Ti configuration preparation amorphous titanium alloy nucleating agent;
(2) melting
(1) step confected materials is put into the water jacketed copper crucible of non-consumable arc furnace, regulate the tungsten electrode position, make it and water jacketed copper crucible in distance between the amorphous titanium alloy nucleating agent raw material put into be 0.5mm, close fire door and purging valve, be evacuated to vacuum tightness force value＞2 * 10
-2Behind the Pa; charging into high-purity argon gas to the force value of vacuum tightness subsequently is 0.06Pa; regulate arc current after the starting the arc and progressively rise to 200A; whole process is all protected with high-purity argon gas; to all raw material fusings; cool to room temperature with the furnace; obtain titan alloy casting ingot; again with the above-mentioned repeatedly fusing and be cooled to the smelting operation process 4 times of room temperature in water jacketed copper crucible of gained titan alloy casting ingot; obtain composition titan alloy casting ingot relatively uniformly, the uniform relatively titan alloy casting ingot of this composition is being evacuated to vacuum tightness＞2 * 10
-3In 900 ℃ of equalizing temperature annealing 7h, make the titan alloy casting ingot of the complete homogenizing of composition in the vacuum annealing furnace of Pa;
(3) centrifugal fast quenching gets rid of band
The titan alloy casting ingot line that (2) is gone on foot the complete homogenizing of composition that makes cuts into fritter, put into the water jacketed copper crucible of vacuum quick quenching furnace, regulate electrode position, make it and water jacketed copper crucible in the titan alloy casting ingot fritter between distance be 0.5mm, close fire door, feed inlet and outlet and purging valve, be evacuated to vacuum tightness force value＞5 * 10
-3Behind the Pa, use ar purging, charging into argon gas to the force value of vacuum tightness subsequently is 0.04Pa, regulate arc current after the starting the arc and progressively rise to 500A, the titan alloy casting ingot fritter is melted, when treating that this titanium alloy fritter all is fused into liquid state, the inclination crucible makes titanium alloy liquid cause on the water-cooled molybdenum wheel of high speed rotating by runner, and the molybdenum wheel surface is 10 ℃, after the fused solution alloy is in contact with it, rapid solidification, molybdenum wheel edge line speed is 35m/ second, and titanium alloy forms thin ribbon shaped and flown out by molybdenum wheel tangential direction, falls into the boxroom of body of heater bottom after baffle plate stops, fast quenching obtains the amorphous titanium alloy band, is the amorphous titanium alloy nucleating agent;
Second step, the preparation of titanium alloy product of aviation fastening piece
(1) configuration titanium alloy substrate raw material
With pure titanium, pure molybdenum, niobium bar, zirconium sponge, pure chromium, fine aluminium and pure vanadium is raw material, amount also by mass percentage for Al:5%, V:6%, Mo:8%, Nb:11%, Zr:1%, Cr:2% and surplus are that Ti takes by weighing above-mentioned all raw materials, is configured to the titanium alloy substrate raw material according to actual needs;
(2) melting and casting
Earlier with the pure titanium, pure molybdenum and the niobium bar raw material that take by weighing in (1) step, by weight being Nb: Ti=4: 1 niobium bar and pure titanium and Mo: Ti=4: 1 pure molybdenum and pure titanium are smelted into NbTi master alloy and MoTi master alloy respectively, and again other all raw materials that take by weighing in (1) step are put into the vacuum shower furnace with above-mentioned NbTi master alloy and MoTi master alloy and carry out the following operation of melting: earlier the vacuum shower furnace being pumped into high vacuum pressure before the melting is 1.2 * 10
-4Pa, charging into argon gas to vacuum shower furnace internal pressure again is 0.1Pa, protects, to all raw material fusings, cool to room temperature with the furnace, obtain titan alloy casting ingot, above-mentioned repeatedly fusing and be cooled to the smelting operation 4 times of room temperature adds weight during smelting operation and is 0.4% the amorphous titanium alloy nucleating agent that is made by the first step of titanium alloy substrate raw material gross weight the last time, cast then, after treating that titanium alloy cools off fully, prepared titan alloy casting ingot is taken out in blow-on;
(3) forge
To forge at 900 ℃ by prepared titan alloy casting ingot of (2) step, reach deflection and be 70% after water-cooled immediately, the deformation of preserving material internal makes and forges the titanium alloy sample of finishing;
(4) water-cooled insulation makes aviation fastening piece titanium alloy product
To put into vacuum tube furnace by the titanium alloy sample that the forging that (3) step makes is finished, be evacuated to vacuum tightness＜0.33Pa, water-cooled is to room temperature behind 700 ℃ of insulation 20min, again this sample is incubated 0.5h at 400 ℃, making elementary composition mass percent is that Al:5%, V:6%, Mo:8%, Nb:11%, Zr:1%, Cr:2% and surplus are the aviation fastening piece titanium alloy product of Ti.
The aviation fastening piece that present embodiment makes has good comprehensive mechanical properties with titanium alloy product, and its tensile strength reaches 1230Mpa, and unit elongation is 10.5%.
Embodiment 2
Preparing elementary composition mass percent is that Al:7%, V:3%, Mo:8%, Nb:13%, Zr:1%, Cr:1% and surplus are the aviation fastening piece titanium alloy of Ti, and its step is as follows:
The first step, preparation amorphous titanium alloy nucleating agent
(1) raw material of configuration preparation amorphous titanium alloy nucleating agent
Mass percent by element is that Cu:13%, Ni:12%, Al:3%, V:3%, Fe:7%, B:3%, Zr:7%, Cr:3% and surplus are the raw material of Ti configuration preparation amorphous titanium alloy nucleating agent;
(2) melting
(1) step confected materials is put into the water jacketed copper crucible of non-consumable arc furnace, regulate the tungsten electrode position, make it and water jacketed copper crucible in distance between the amorphous titanium alloy nucleating agent raw material put into be 1mm, close fire door and purging valve, be evacuated to vacuum tightness force value＞2 * 10
-2Behind the Pa; charging into high-purity argon gas to the force value of vacuum tightness subsequently is 0.07Pa; regulate arc current after the starting the arc and progressively rise to 250A; whole process is all protected with high-purity argon gas; to all raw material fusings; cool to room temperature with the furnace; obtain titan alloy casting ingot; again with the above-mentioned repeatedly fusing and be cooled to the smelting operation process 5 times of room temperature in water jacketed copper crucible of gained titan alloy casting ingot; obtain composition titan alloy casting ingot relatively uniformly, the uniform relatively titan alloy casting ingot of this composition is being evacuated to vacuum tightness＞2 * 10
-3In 1000 ℃ of equalizing temperature annealing 8h, make the titan alloy casting ingot of the complete homogenizing of composition in the vacuum annealing furnace of Pa;
(3) centrifugal fast quenching gets rid of band
The titan alloy casting ingot line that (2) is gone on foot the complete homogenizing of composition that makes cuts into fritter, put into the water jacketed copper crucible of vacuum quick quenching furnace, regulate electrode position, make it and water jacketed copper crucible in the titan alloy casting ingot fritter between distance be 1.0mm, close fire door, feed inlet and outlet and purging valve, after being evacuated to vacuum tightness force value＞5 * 10-3Pa, use ar purging, charging into argon gas to the force value of vacuum tightness subsequently is 0.045Pa, regulate arc current after the starting the arc and progressively rise to 550A, with the fusing of titan alloy casting ingot fritter, when treating that this titanium alloy fritter all is fused into liquid state, the inclination crucible makes titanium alloy liquid cause on the water-cooled molybdenum wheel of high speed rotating by runner, the molybdenum wheel surface is 13 ℃, after the fused solution titanium alloy is in contact with it, rapid solidification, molybdenum wheel edge line speed is 42m/ second, titanium alloy forms thin ribbon shaped and is flown out by molybdenum wheel tangential direction, fall into the boxroom of body of heater bottom after baffle plate stops, fast quenching obtains the amorphous titanium alloy band, is the amorphous titanium alloy nucleating agent;
Second step, the preparation of titanium alloy product of aviation fastening piece
(1) configuration titanium alloy substrate raw material
With pure titanium, pure molybdenum, niobium bar, zirconium sponge, pure chromium, fine aluminium and pure vanadium is raw material, amount also by mass percentage for Al:7%, V:3%, Mo:8%, Nb:13%, Zr:1%, Cr:1% and surplus are that Ti takes by weighing above-mentioned all raw materials, is configured to the titanium alloy substrate raw material according to actual needs;
(2) melting and casting
Earlier with the pure titanium, pure molybdenum and the niobium bar raw material that take by weighing in (1) step, be Nb: Ti=4 by weight: 1 niobium bar and pure titanium and Mo: Ti=4: 1 pure molybdenum and pure titanium are smelted into NbTi master alloy and MoTi master alloy respectively, again other all raw materials that take by weighing in (1) step being put into the vacuum shower furnace with above-mentioned NbTi master alloy and MoTi master alloy and carry out the following operation of melting, is 2.0 * 10 with being pumped into high vacuum pressure in the vacuum shower furnace earlier before the melting
-4Pa, charging into argon gas to vacuum shower furnace internal pressure again is 0.3Pa, protects, to all raw material fusings, cool to room temperature with the furnace, obtain titan alloy casting ingot, above-mentioned repeatedly fusing and be cooled to the smelting operation 5 times of room temperature adds weight during smelting operation and is 0.4% the amorphous titanium alloy nucleating agent that is made by the first step of titanium alloy substrate raw material gross weight the last time, cast then, after treating that titanium alloy cools off fully, prepared titan alloy casting ingot is taken out in blow-on;
(3) forge
To forge at 1000 ℃ by prepared titan alloy casting ingot of (2) step, reach deflection and be 100% after water-cooled immediately, the deformation of preserving material internal makes and forges the titanium alloy sample of finishing;
(4) water-cooled insulation makes aviation fastening piece titanium alloy product
To put into vacuum tube furnace by the titanium alloy sample that the forging that (3) step makes is finished, be evacuated to vacuum tightness＜0.33Pa, water-cooled is to room temperature behind 820 ℃ of insulation 20min, again this sample is incubated 2.6h at 470 ℃, making elementary composition mass percent is that Al:7%, V:3%, Mo:8%, Nb:13%, Zr:1%, Cr:1% and surplus are the aviation fastening piece titanium alloy product of Ti.
The aviation fastening piece that present embodiment makes has improved comprehensive mechanical performance with titanium alloy product than embodiment 1, and its tensile strength reaches 1370Mpa, and unit elongation is 11.6%.
Embodiment 3
Preparing elementary composition mass percent is that Al:9%, V:1%, Mo:8%, Nb:15%, Zr:1%, Cr:0.1% and surplus are the aviation fastening piece titanium alloy of Ti, and its step is as follows:
The first step, preparation amorphous titanium alloy nucleating agent
(1) raw material of configuration preparation amorphous titanium alloy nucleating agent
Mass percent by element is that Cu:15%, Ni:10%, Al:5%, V:1%, Fe:10%, B:1%, Zr:10%, Cr:1% and surplus are the raw material of Ti configuration preparation amorphous titanium alloy nucleating agent;
(2) melting
(1) step confected materials is put into the water jacketed copper crucible of non-consumable arc furnace, regulate the tungsten electrode position, make it and water jacketed copper crucible in distance between the amorphous titanium alloy nucleating agent raw material put into be 1.5mm, close fire door and purging valve, be evacuated to vacuum tightness force value＞2 * 10
-2Behind the Pa; charging into high-purity argon gas to the force value of vacuum tightness subsequently is 0.08Pa; regulate arc current after the starting the arc and progressively rise to 300A; whole process is all protected with high-purity argon gas; to all raw material fusings; cool to room temperature with the furnace; obtain titan alloy casting ingot; again with the above-mentioned repeatedly fusing and be cooled to the smelting operation process 6 times of room temperature in water jacketed copper crucible of gained titan alloy casting ingot; obtain composition titan alloy casting ingot relatively uniformly, the uniform relatively titan alloy casting ingot of this composition is being evacuated to vacuum tightness＞2 * 10
-3In 1100 ℃ of equalizing temperature annealing 7h～10h, make the titan alloy casting ingot of the complete homogenizing of composition in the vacuum annealing furnace of Pa;
(3) centrifugal fast quenching gets rid of band
The titan alloy casting ingot line that (2) is gone on foot the complete homogenizing of composition that makes cuts into fritter, put into the water jacketed copper crucible of vacuum quick quenching furnace, regulate electrode position, make it and water jacketed copper crucible in the titan alloy casting ingot fritter between distance be 0.5mm～1.5mm, close fire door, feed inlet and outlet and purging valve, be evacuated to vacuum tightness force value＞5 * 10
-3Behind the Pa, use ar purging, charging into argon gas to the force value of vacuum tightness subsequently is 0.04Pa～0.05Pa, regulate arc current after the starting the arc and progressively rise to 500A～600A, the titan alloy casting ingot fritter is melted, when treating that this titanium alloy fritter all is fused into liquid state, the inclination crucible makes titanium alloy liquid cause on the water-cooled molybdenum wheel of high speed rotating by runner, the molybdenum wheel surface is 10 ℃～15 ℃, after the fused solution titanium alloy is in contact with it, rapid solidification, molybdenum wheel edge line speed is second 35m/ second～50m/, and titanium alloy forms thin ribbon shaped and flown out by molybdenum wheel tangential direction, falls into the boxroom of body of heater bottom after baffle plate stops, fast quenching obtains the amorphous titanium alloy band, is the amorphous titanium alloy nucleating agent;
Second step, the preparation of titanium alloy product of aviation fastening piece
(1) configuration titanium alloy substrate raw material
With pure titanium, pure molybdenum, niobium bar, zirconium sponge, pure chromium, fine aluminium and pure vanadium is raw material, according to actual needs amount and be 9% by mass percentage, V:1%, Mo:8%, Nb:15%, Zr:1%, Cr:0.1% and surplus be that Ti takes by weighing above-mentioned all raw materials, is configured to the titanium alloy substrate raw material;
(2) melting and casting
Earlier with the pure titanium, pure molybdenum and the niobium bar raw material that take by weighing in (1) step, by weight being Nb: Ti=4: 1 niobium bar and pure titanium and Mo: Ti=4: 1 pure molybdenum and pure titanium are smelted into NbTi master alloy and MoTi master alloy respectively, and again other all raw materials that take by weighing in (1) step are put into the vacuum shower furnace with above-mentioned NbTi master alloy and MoTi master alloy and carry out the following operation of melting: earlier the vacuum shower furnace being pumped into high vacuum pressure before the melting is 2.7 * 10
-4Pa, charging into argon gas to vacuum shower furnace internal pressure again is 0.5Pa, protects, to all raw material fusings, cool to room temperature with the furnace, obtain titan alloy casting ingot, above-mentioned repeatedly fusing and be cooled to the smelting operation 6 times of room temperature adds weight during smelting operation and is 0.4% the amorphous titanium alloy nucleating agent that is made by the first step of titanium alloy substrate raw material gross weight the last time, cast then, after treating that titanium alloy cools off fully, prepared titan alloy casting ingot is taken out in blow-on;
(3) forge
To forge at 1100 ℃ by prepared titan alloy casting ingot of (2) step, reach deflection and be 120% after water-cooled immediately, the deformation of preserving material internal makes and forges the titanium alloy sample of finishing;
(4) water-cooled insulation makes aviation fastening piece titanium alloy product
To put into vacuum tube furnace by the titanium alloy sample that the forging that (3) step makes is finished, be evacuated to vacuum tightness＜0.33Pa, water-cooled is to room temperature behind 950 ℃ of insulation 20min, again this sample is incubated 5h at 550 ℃, making elementary composition mass percent is that Al:9%, V:1%, Mo:8%, Nb:15%, Zr:1%, Cr:0.1% and surplus are the aviation fastening piece titanium alloy product of Ti.
The aviation fastening piece that present embodiment makes has improved comprehensive mechanical performance with titanium alloy product than embodiment 1, and its tensile strength reaches 1390MPa, and unit elongation is 11.7%.
Among above-mentioned all embodiment, the section area of the sample before described deflection=(section area of the sample after the section area-forging of the sample before forging)/forging.
Among above-mentioned all embodiment, related raw material, technology and equipment all are that metallurgical technology field is known and know.
Claims (2)
1. aviation fastening piece titanium alloy, it is characterized in that: its elementary composition mass percent is that Al:5%～9%, V:1%～6%, Mo:8%, Nb:11%～15%, Zr:1%, Cr:0.1%～2% and surplus are Ti.
2. the described aviation fastening piece of claim 1 is characterized in that step is as follows with the preparation method of titanium alloy:
The first step, preparation amorphous titanium alloy nucleating agent.
(1) raw material of configuration preparation amorphous titanium alloy nucleating agent
Mass percent by element is that Cu:10%～15%, Ni:10%～15%, Al:1%～5%, V:1%～5%, Fe:3%～10%, B:1%～5%, Zr:5%～10%, Cr:1%～5% and surplus are the raw material of Ti configuration preparation amorphous titanium alloy nucleating agent;
(2) melting
(1) step confected materials is put into the water jacketed copper crucible of non-consumable arc furnace, regulate the tungsten electrode position, make it and water jacketed copper crucible in distance between the amorphous titanium alloy nucleating agent raw material put into be 0.5mm～1.5mm, close fire door and purging valve, be evacuated to vacuum tightness force value＞2 * 10
-2Behind the Pa; charging into high-purity argon gas to the force value of vacuum tightness subsequently is 0.06Pa～0.08Pa; regulate arc current after the starting the arc and progressively rise to 200A～300A; whole process is all protected with high-purity argon gas; to all raw material fusings; cool to room temperature with the furnace; obtain titan alloy casting ingot; again with the above-mentioned repeatedly fusing and be cooled to the smelting operation process 4 times～6 times of room temperature in water jacketed copper crucible of gained titan alloy casting ingot; obtain composition titan alloy casting ingot relatively uniformly, the uniform relatively titan alloy casting ingot of this composition is being evacuated to vacuum tightness＞2 * 10
-3In 900 ℃～1100 ℃ equalizing temperature annealing 7h～10h, make the titan alloy casting ingot of the complete homogenizing of composition in the vacuum annealing furnace of Pa;
(3) centrifugal fast quenching gets rid of band
The titan alloy casting ingot line that (2) is gone on foot the complete homogenizing of composition that makes cuts into fritter, put into the water jacketed copper crucible of vacuum quick quenching furnace, regulate electrode position, make it and water jacketed copper crucible in the titan alloy casting ingot fritter between distance be 1.5mm, close fire door, feed inlet and outlet and purging valve, be evacuated to vacuum tightness force value＞5 * 10
-3Behind the Pa, use ar purging, charging into argon gas to the force value of vacuum tightness subsequently is 0.05Pa, regulate arc current after the starting the arc and progressively rise to 600A, the titan alloy casting ingot fritter is melted, when treating that this titanium alloy fritter all is fused into liquid state, the inclination crucible makes titanium alloy liquid cause on the water-cooled molybdenum wheel of high speed rotating by runner, and the molybdenum wheel surface is 15 ℃, after the fused solution titanium alloy is in contact with it, rapid solidification, molybdenum wheel edge line speed is 50m/ second, and titanium alloy forms thin ribbon shaped and flown out by molybdenum wheel tangential direction, falls into the boxroom of body of heater bottom after baffle plate stops, fast quenching obtains the amorphous titanium alloy band, is the amorphous titanium alloy nucleating agent;
Second step, the preparation of titanium alloy product of aviation fastening piece.
(1) configuration titanium alloy substrate raw material
With pure titanium, pure molybdenum, niobium bar, zirconium sponge, pure chromium, fine aluminium and pure vanadium is raw material, amount also by mass percentage for Al:5%～9%, V:1%～6%, Mo:8%, Nb:11%～15%, Zr:1%, Cr:0.1%～2% and surplus are that Ti takes by weighing above-mentioned all raw materials, is configured to the titanium alloy substrate raw material according to actual needs;
(2) melting and casting
Earlier with the pure titanium, pure molybdenum and the niobium bar raw material that take by weighing in (1) step, by weight being Nb: Ti=4: 1 niobium bar and pure titanium and Mo: Ti=4: 1 pure molybdenum and pure titanium are smelted into NbTi master alloy and MoTi master alloy respectively, and again other all raw materials that take by weighing in (1) step are put into the vacuum shower furnace with above-mentioned NbTi master alloy and MoTi master alloy and carry out following smelting operation: earlier the vacuum shower furnace being pumped into high vacuum pressure before the melting is 1.2 * 10
-4Pa～2.7 * 10
-4Pa, charging into argon gas to vacuum shower furnace internal pressure again is 0.1Pa～0.5Pa, protects, to all raw material fusings, cool to room temperature with the furnace, obtain titan alloy casting ingot, above-mentioned repeatedly fusing and be cooled to the smelting operation 4～6 times of room temperature adds weight during smelting operation and is 0.4% the amorphous titanium alloy nucleating agent that is made by the first step of titanium alloy substrate raw material gross weight the last time, cast then, after treating that titanium alloy cools off fully, prepared titan alloy casting ingot is taken out in blow-on;
(3) forge
To forge at 900 ℃～1100 ℃ by prepared titan alloy casting ingot of (2) step, reach deflection and be 70%～120% after water-cooled immediately, the deformation of preserving material internal makes and forges the titanium alloy sample of finishing;
(4) water-cooled insulation makes aviation fastening piece titanium alloy product
To put into vacuum tube furnace by the titanium alloy sample that the forging that (3) step makes is finished, be evacuated to vacuum tightness＜0.33Pa, water-cooled is to room temperature behind 700 ℃～950 ℃ insulation 20min, again this sample is incubated 0.5h～5h at 400 ℃～550 ℃, making elementary composition mass percent is that Al:5%～9%, V:1%～6%, Mo:8%, Nb:11%～15%, Zr:1%, Cr:0.1%～2% and surplus are the aviation fastening piece titanium alloy product of Ti.
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